Aircraft and airplane construction



May 8, 1928.

W. CHALMERS AIRCRAFT AND AIRPLANE CONSTRUCTION l S'Sheets-Sheet 1 FiledFeb. 13. 1925 ATTORNEYS May 8, 1928. 1,868,889

W. CHALMERS AIRGRAF'11 AND AIRPLANE CONSTRUCTION Filed Feb.1s. 1926 5Sheets-Sheet 2 L im?? y@ May 8, 1928.

W. CHALMERS AIRCRAFT AND AIRPLANE CONSTRUCTION Filed Feb. 15. 1926 5Sheets-Sheet 5 FCS INVENTOR William C ATTORNEYS BWMLM 1%,

WITNESSES May 8, 1928.

W. CHALLMERS AIRCRAFT AND AIRPLANE CONSTRUCTION May 8, 1928.

w. cHALMx-:RS

AIRCRAFT AND AIRPLANE CONSTRUCTION Filed Feb. 15. 1926 5 Sets-Sheet 5 fINVENTOR M f l L t ATTORNEYS Patented May 8, 1928.

UNITED STATES WILLAM CHALMERS, OF SACRAMENTO, CALIFORNIA.

AIRCRAFT ANI) AIRPLANE CONSTRUCTION.

Application led February 13, 1926, Serial No. 88,073.

This invention relates in general to flying machines of the heavier thanair type an more particularly to an air craft which combines thequalities of an air aeroplane and a helicopter.

The object of the invention resides in the provision of an air craft ofthis character which is of compact and symmetrical form to the ends ofconvenience in storage and l0 balance in flight, which is of greatcarrying power and high maneuvering ability, and which is capable ofdeveloping a high speed in flight and also capable of approximatehovering over any desired point.

A further 'object is, by suitable disposition of planar surface in andwith relation to the slipstream to secure a greater degree of supporttherefrom and also a steadying effect by control of the lateral escapeof slipstream air 'in flight. v

A still further object is the provision of a novel form ofvariablesustaining surface capable of shedding snow.

Another object is to provide an 'air craft of this character which iscapable of near apw preach to a vertical take-olf and of safe and easylanding on Small areas.` f

Other objects and advantages reside in certain novel features of theconstruction, arrangement and combination of parts which will behereinafter more fully described and particularly pointed out in theappended claim, reference being had to the accompanying drawings forminga part of this specification, and in which:

Figure 1 is a fragmentary view in longitudinal vertical section taken onthe line l--l .of Figure 2 and showing the major portion of the aircraftembodying the present invention,

Figure 1a is a fragmentary view similar to v Figure 1 but showing theextreme rear end of the air craft shown in Figure 1,

Figure 2 is a view in transverse vertical section taken on line 2-2 ofFigure 1,

Figure 3 is a view in horizontal section on line' 3--3 of Figure 2;

Figure 3 is a fragmentary view similar to Figure 3 but showingtheeXtreme rear,

end of the air cra-ft,

Figure 4 is a detail perspective view of the framing employed, thestruts and braces being omitted,

Figure 5 1s a detail sectional view on line '5--5 of Figure 2,

Figure 6 is a similarview on line 6-6- of Figure 5,

Figure 7 is a sectional view on line 7-7 of Figure 2,

. Figure 8 is a sectional view on line 8-8 of Figure 3,

Figure 9 is a sectional view on line 9-9 of Fig. 4,

Figure 10 is a fragmentary detailed view in perspective illustrating theinternal vane structure, and

Figure 1,1 is a fragmentary view, partly in elevation and partly insection, showing how the vanes are mounted on top rails 26 to provide anopen or military type of ceiling.

Referring to the drawings wherein for the sake of illustration is shownan embodiment of the invention, it will be seen that a suitable frame isprovided. One type of frame which may be employed is shown to advantagein Figure 4 and is made up of end frame members designated generally at1 and 2, andl an intermediate frame member designated generally at 3.The frame members l, 2 and 3 are of identical construct-ion and eachlframe member is approximately U-shaped and comprises a body portion 4and diverging legs 5. The frame members may be constructed of metalpiping or of tubular elements of any `suitable material, and the bodyportions and legs of the frame members are coupled in any suitable way.Longitudinal side bars 6 are suitably coupled to the frame members atthe juncture of the legs and body portions thereof. As shown in Figure 9an Vattaching plate 7 is suitably fastened to the upper end ofeach leg5. Preferably this fastening of each leg 5 and its plate 7 is broughtabout by externally threading the vertical upper end of each leg 5 as at5a and engaging such threaded end with an internally threaded socket 7ELformed on and depending from its attaching plate 7. Side rails 8 rest onthe attaching plates 7 of the legs 5 on each side of the frame and theseside rails are secured to the attaching plates onl which they rest bymeans of U- bolts or clips 9 and nuts 10. The side rails 8 arepreferably of wood and are provided with a light weight sheet metalcasing 8. The ends of the side rails project beyond the end framemembers 5 and these projecting vends are braced or supported by means ofthe inclined braced members 11, the brace members 11 being secured attheir lower ends to the frame members. Attaching plates 7 are alsoprovided at the upper ends -of the brace members 11 and are also securedto the side rails by means of U-bolts or clips 9 and nuts 10.

Front end posts 15, rear end posts 16, and

posts 15 and 16, each of the elements of each double post and each ofthe top rails 18 consists of a piece of wood 19 with one round edge andencased on three sides in a metal sheathingl 20 secured to the Wood byrivets or suitable fastening devices. The portion of the metal sheathingwhich is located on the outside of each post is extended at its endsbeyond the posts as indicated at 2l to overlap the adjacent top or siderails as the case may be and to aid in securing the posts and rails toeach other. Attaching plates 22 are provided at the juncture of theposts and side and top rails and each attaching plate is arranged on theinside'of the fra-me and is secured by suitable fastening devices y 23to both the posts and rails. .The fastening devices 23 which co-act withthe side and top rails and plates 22 also extend through the extensions21. As shown in Figure 9, the plates 22 retain internally threadedsockets 24 and the sockets 24 of oppositely disposed plates 22 arethreadedly engaged with the externally threaded ends of transverse bracebars 25. As shown in the drawings the brace bars 25 extend between the`side rails and the top rails above and below opposed posts.l A pair ofintermediate top rails 26 are carried by the upper transverse brace bars25 and are fastened thereto in fixed parallel relation as by means ofthe bolts or clips 27, plates 28 and nuts 29.y Like the posts 15, 16 and17 and top rails 18 the intermediate top rails 26 are made up of piecesof wood and metal sheathing.

However, tubular metallic elements may bel used if desirable.

On the top and sidesV of the frame thus constituted, a number of vanesare mounted as will be hereinafter more fully described and these vanesprovide the sustaining or reactive surface of the air craft and withother vanes also control the lateral escape of the slipstream to steadyand stabilize the craft. The vanes provided on the top of the framing`are arranged in two groups or series, there being a group or series 30at the front of the machine and a Lgroup or series 31 at the rear of themachine (see Fig.

1). The vanes of the groups or series 30 and 31 are mounted on parallelaxes extending transversely of the machine and disposed in a horizontalplane. The vanes arranged on the sides of the frame are also provided ingroups or series, there being a forward group 34 and a rearward group 35on each side of the machine. The forward series 34 at each side extendsbetween and is assembled with the front corner post on its side and thefront section of central post 17 and the rear series on each sideextends between and is assembled with the rear corner post and the rearsection of the central post. The vanes 34 and 35 are mounted on parallelaxes extended longitudinally of the machine and located one above theother in a vertical plane. Intermediate their ends the vanes 34 and 35are partially cut away, as at 34a and 35 to accommodate the braces 14(see Fig. 3). In addition to thevanes 34 and 35 on each side of themachine, inclined series of vanes 36 are provided on the side of themachine and are carried by the diverging legs5 ofthe frame members.

All of the vanes are of identical construction with the exception of thenecessary modifications made in several of the vanes for the operatingand idling sprockets and as shown in Figure 10 each includes a tubularshaft or axis 40. At spaced intervals upon the shaft or axis 40 pairs ofmetallic strips 41 are brazed, soldered, or welded,

or otherwise suitably secured, the strips 41 or metallic coveringextends around and encloses the vane framework thus constituted.

'The top vanes 30 and 31 have pintles 45 at' the ends of their shafts40, the pintles 45 rotatably fitting in bearings 47 provided therefor inthe top rails 18 and the shafts 46 rot tably fitting in bearings 48provided therefor on the undersides of the intermediate top rails.

lll

The side vanes 34 and 35'have pintles 45 at v both ends of their shafts40, the pintles 45 of the vanes 34 and 35 being rotatably fitted insuitable bearings provided therefor in the posts y15, 16 and 17. Theportions of the shafts 40 of 'these vanes 34 and 35 which arecomprehended within the cutaway portions 34 and 35aare rotatably fittedin bearings 49 providedr therefor on the vertical braces 14 (see Fig.

The vanes 36 also have pintles 45 (see Fig. 7) at the ends of theirshafts 40 and these pintles 45 are rotatably fitted in bearings 50provided therefor in blocks 51 secured by U-bolts or clips 52, plates 53and nuts 54 to the legs 5 of the'frame members 1 and 2. The vanes 36also have cut-away portions 36a (see Fig. 3) which accommodate .the legs5-of the--intermediateframe member 3 whichl carries thebearings forshaft 40.

rI he vanes of all of the series are designed in the position parallelto each other to leave open spaces between the vanes or they aredesigned to be brought into edge to` edge relation or into'such positionthat the edges of the adjacent vanes slightly overlap each other. Ofcourse, the vanes may also be moved to any position of intermediate `ets60. Sprocket chains 61 are trained over the sprocket 60 and over idlers62 (see Fig. 2) loosely mounted on the shafts or axesof vanes of theseries 30. The sprocket chains c 61 are also trained over controlsprocket wheels 63 fixed on the ends of a control shaft 64..The'sprocket chains 61 are also run over idlers 65 carried by shafts 66amounted on brackets 66. Levers 67 are fixed to the shaft 64 and,serve asmeans for imparting movement to the shaft. It is to be understood thata. quadrant and lever latch may be employed in conjunction with eachlever 67 ifdesired and also in conjunction with the other levershereinafter to be described. Connecting links 75 (see Fig. are pivotallyconnected to all of the vanes of the Iseries 31 and serve to constrainall of the vanes to corresponding movement so that a -movementimpartedto one vane of each of the series 31 and from the lever 67 is impartedto all of the vanes of both such series.

One vane of the series 30 has sprocket wheels 70 fixed thereto.'Sprocket chains 71 are trained over sprocket wheels 70 and overcontrolled sprocket Wheels 72 fixed to the ends of a sleeve controlshaft-,.7 3 rotatably mounted on theshaft 64. Hand levers 74 are fixedto the sleeve 73 and provide'` means for controlling and movingthe same.The vanes of the series 30 are also constrained to correspondingmovement by virtue of the provision of links 75 pivotally connected tothe vanes of such series.

The vanes of the series 30 and 31 provide the main sustaining surfacesof the air craft and may be adjusted to vary the degree and character ofthe sustaining action. The

vanes are cut away to accommodate the top rails 26. Fig. 2 shows thisfeature in connection with the vanes 30. 1

- The vanes of the series 34'and 35` y con trolled from shafts byl meansof s` ocket chains 81 trained over sprocket wheels 82 fixed to theshafts 80 and over sprocket wheels 83 fixed to the ends of the shaft 40of one of the vanes of veach series. The shafts 80 are controlled bymeans of an endless sprocket chain 84 trained over sprockets 80a fixedto the shafts 80 and actuated from a control sprocket 85 having a handlever 86 fixed thereto. Links 87 are pivotally connected to the vanes ofthe series 34 and 35 for the purpose of constraining these vanes tocorresponding movement.

The inclined series of vanes 26 are controlled from a sprocket chain 90trained over sprocket wheels -91 fixed to a vane of each of the series36 and is self-controlled 'from a tiller92 pivotally mounted on a collar92a loosely fitted on the shaft 73 as shown in Figs. 5 and 6. Links 94are provided and are pivotally connected to the vanes 36 to constrainthem to corresponding movement.

The vanes34, 35 and 36 may be adjusted to vary the sustaining effect tosome extent and also to control the escape of the slipstream andprovideineans for lateral balancing.

Elevators are rotatably mounted on the rear end cross bar 25 whichconnects the lower ends of the corner post. Cross arms 101 are connectedwith the elevators 100 and have control wires 102 connected to theirends and to arms 103 of a control shaft 103 journaled on a suitablefuselagel 105 mounted on the frame. controlled by levers 104.

A rudder 106 is pivotally mounted at the. rear end of the fuselage andhas a sprocket wheel107 fixed to its axis and controlled from a steering`-column 93 by means of a sprocket wheel 108 and sprocket chain 109trained over the sprocket wheels 108 and 107. It is to be understoodthat the control wires and sprocket chains described herein may beconstituted by any suit-able flexible elements and that these controlwires and sprocket chains may be extended through guide tubes orconduits over guide sheaves. and also through or around the fuselage asfound most convenient.

A running gear is provided and comprises a pair of front ground wheels110 and a single rear steering wheel 111. IThe steer.- ing wheel 111 isrotatably mounted on a wheel frame 112 to which a king bolt 113 isfixed. The king bolt 113 isfixedly secured to a bea-ring plate 114having limited rotary movement in a bearing ring 114*L and is controlledby means of a sprocket Wheel 115 and a sprocket chain 116, the sprocketchain 116 being trained over the sprocket wheel The shaft 103 isv llO'bevelled gea 115 and over a sprocket wheel 117 fixed to the steeringcolumn 93. Brace members 118 are connected to the wheel frame, as at 120and with the bearing plate 114, as at 121. The rotary movement of thebearing plate 114 and its ring 114a`is limited by slots 122 and boltsand nuts 123 for which see Fig. 3.

The arrangement shown wherein there is provided a. common control forthe steering Wheel of the landing gear or running gear and for therudder is an important feature of the invention, for with thisarrangement the steering Wheel 111 supplements the action of the rudderin flight and the advantage of a singlecontrol for the steering wheeland rudder is had at all times.

An improved aeroplane engine 125 is provided /and the forward end ofthis engine shaft 126 has a conventional propeller127 fixed thereto, thepropeller 127 rotating in a vertical plane and serving to pull the aircraft along the line of flight. The engine 125 is also equipped with aclutch and selective transmission gear 128 which connects with the rearend of the engine shaft to actuate andd '.ve the shaft 129 connected byis 130 with a vertical shaft 131, to the lower end of which a horizontalpropeller 132 is fixed.` By an adjustment of the vanes of the series 30and 31 and the joint operation of the horizontal and vertical propellersit is possible to obtain an approximately vertical take-ofi' and slowspeed or hovering fiight and a safe landing on small areas.

The fuselage may be provided withl seats, bulk heads and any of theother features ordinarily used and suitable to the present type ofconstruction. The feature of constituting the major sustaining surfaceof adjacent vanes which may be inovedto provide a continuous unbrokensustaining surface is one of the principal features of the invention;for an inclined setting of the vanes in conjunction with the provisionof the horizontal propeller as -well as the vertical propeller enablesalmostvertical ascent to be had. Provision of the side vanes and of theinclined vanes enhances the maneuvering capacity of the air craft andalso aids l its stability, since it enables the air craft to availitself of the forces of the slipsti'eam heretofore unused. The provisionof the adj ustable vanes of the sustaining surface and on the sides alsoenables the air craft to shed snow and hail that might otherwiseaccuinulate thereon. This same feature admits clear and unobstructedviewv and the possibility of directing gun fire through the top of theplane as well as through the side and bottom thereof. It is also to benoted that the main sustaining surface of the air craft has its greatestdimension in the line of flight land this is believed to be a featurelending to safety, stability and economy of construction.

As shown in'Figure 11 instead of having the vanes extend entirely acrossthe machine the vanes may be provided in groups at each yside of themachine, as indicated at 30u and 30b in Fig. 11, the vanes in this eventbeing pivotally mounted on the top rails 26, as shown in Figure 11,thereby leaving between the rails 26 an open' space O. This isespecially desirable to accommodate gun fire when the air craft orairplane is used for military purposes. The construction of the vanesand their operations is the sameas in the embodiment of the inventionhereinabove described.

While the open centered ceiling is shown as most favorable for militaryuse, it is obvious that a closed ceilin having one or more overheadbearings will be preferable for commercial use, while vanes supported attheir ends only would serve for smaller forms of aircraft.

In practice it will probably be desirable to position the top rails 26between the chains 61 alid 71. If desired, the rails 26 may be placedbetween the chains 61 and 71, the spacing of the parts being varied, asnecessary.

I claim:

An air craft including a. frame, adjustable vanes mounted on the top ofthe frame and providing a inainsustaining surface to the air craft,means for controlling the position of said vanes, series of vanesarranged on the sides of the frame, ce tain of said series inclininginwardly, means for controlling the position ofthe vanes on the sides ofthe frame, and propelling means for the air craft including a horizontaland a vertical propeller. l WILLIAM CHALMERS.

